WO2015037954A1 - Système d'isolation de petite vibration de refroidisseur pour espace ayant une fonction de réduction de vibrations dans un environnement de lancement - Google Patents

Système d'isolation de petite vibration de refroidisseur pour espace ayant une fonction de réduction de vibrations dans un environnement de lancement Download PDF

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Publication number
WO2015037954A1
WO2015037954A1 PCT/KR2014/008553 KR2014008553W WO2015037954A1 WO 2015037954 A1 WO2015037954 A1 WO 2015037954A1 KR 2014008553 W KR2014008553 W KR 2014008553W WO 2015037954 A1 WO2015037954 A1 WO 2015037954A1
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WO
WIPO (PCT)
Prior art keywords
vibration
string
fixed shaft
displacement
head
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Ceased
Application number
PCT/KR2014/008553
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English (en)
Korean (ko)
Inventor
오현웅
권성철
전수현
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Chosun University Industry Academic Cooperation Foundation
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Chosun University Industry Academic Cooperation Foundation
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Publication of WO2015037954A1 publication Critical patent/WO2015037954A1/fr
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Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/38—Guiding or controlling apparatus, e.g. for attitude control damping of oscillations, e.g. nutation dampers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/228—Damping of high-frequency vibration effects on spacecraft elements, e.g. by using acoustic vibration dampers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F1/00—Springs
    • F16F1/36—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers
    • F16F1/42—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers characterised by the mode of stressing
    • F16F1/44—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers characterised by the mode of stressing loaded mainly in compression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
    • F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal

Definitions

  • the present invention relates to a space cooler micro-vibration isolation system having a vibration reduction function of the launch environment, and more specifically, to improve the directivity of an observation satellite requiring high resolution observation performance in space, such as a space cooler.
  • the present invention relates to a space cooler micro-vibration isolation system having a vibration reduction function of a launch environment that prevents vibrations generated from a source from being transmitted to mission equipment of an observation satellite.
  • mission equipment of satellites is equipped with an infrared detector which is used for observation of the ground with visible light, and cryogenic cooling of the detector detection surface is essential for obtaining infrared images from it. Used.
  • the observation-oriented performance is deteriorated, which inevitably degrades the image quality.
  • the observation satellite is inevitably equipped with a reaction wheel (actuator) for controlling the attitude of the satellite, the mission equipment of the observation satellite is also adversely affected by the minute vibration caused by the reaction wheel driving.
  • the vibration isolation performance is met by vibration isolators supporting mission equipment.
  • the vibration isolator adopts a relatively low rigidity support structure due to the uniqueness of satellites, especially observation satellites.
  • the support structure of the vibration isolator is formed to have a relatively low rigidity, it is suitable for the track environment, but securing structural health is relatively disadvantageous in a launch environment different from the track environment. Therefore, the mission equipment of the observation satellite has a dual structure that is protected by a separate launch control device together with the vibration isolator of the low rigidity support structure.
  • the mission equipment of the observation satellite is protected by a vibrating isolator having a low rigidity support structure in an orbital environment, and in a launch environment by a separate launch control device that reinforces the weak supporting rigidity of the vibrating isolator.
  • the structural integrity of the satellite system cannot be avoided, but the launching restraint device is inevitable.
  • the function of the vibration isolator cannot be realized when the operation of the sensor is not performed, which causes the failure of the acquisition of the high resolution image information due to the degradation of the directivity of the observation satellite by the vibration transmission from the cooler which is the vibration source.
  • the vibration isolation module disclosed in the above patent has a limit in reducing the vibration component applied from the strong impact in the launch environment, so that the shock vibration in the launch environment still remains.
  • the vibration source is supported by the low rigidity spring support structure to reduce micro vibrations in the gravity-free orbit environment, and the natural frequency from the vibration source and the vibration isolator has a main frequency of the vibration source itself ( It is composed of the principle of isolating vibration by positioning at a frequency lower than the excitation frequency, the spring disclosed in the prior patent for vibration attenuation in the launch environment where the vibration environment is more severe than the track environment where the micro vibration is subject to vibration isolation The problem is that it is insufficient to play a role.
  • the present invention has been made in view of the above point, it is to reduce the vibration component applied from the strong impact in the launch environment, and at the same time to reduce the vibration environment of the launch environment to insulate the micro vibrations generated in the orbit environment.
  • the purpose of the present invention is to provide a space cooler micro-vibration insulation system provided.
  • the space cooler microvibration isolation system having a vibration reduction function of the launch environment includes: a fixed shaft 100 having one end fixedly connected to a vibration source mounted on a satellite; It is installed to surround the fixed shaft 100 in the axial direction, the axial displacement constraint body 31 made of a hollow cylindrical shape, and extends at both ends of the axial displacement constraint body 31 and the axial displacement constraint body 31
  • the shaft displacement 32 of the fixed shaft cover 30 penetrates, but the shaft displacement constraint body 31 is not formed through the plane displacement constraint hole 21 is formed in the center portion, one side of the shaft displacement constraint body ( A displacement confinement block 20 in contact with the end of the 31; A head 11 coupled to the displacement confinement block 20 and having an accommodation space accommodating the axial displacement constraining body 31 of the fixed shaft cover 30 therein, and a predetermined angle from the head 11.
  • a support bracket 10 including left and right legs 13 and 14 extending to open; And mounted to an outer surface of the head 11 of the support bracket 10 so as to be disposed radially with respect to the axial displacement restraint body 31 of the fixed shaft cover 30, and the outer side of the axial displacement restraint body 31.
  • the string 45 is circumferentially wrapped and has a predetermined tensile force, and is connected to the string 45 passing through the string through hole 19 formed in the head 11 of the support bracket 10.
  • 45 includes a damper unit 40 including a damper unit for absorbing vibration generated from the fixed shaft 100.
  • the damper unit of the damper unit 40, the damping element 41 penetrates the string 45, one side of the damping unit 41 in contact with the outer surface of the head (11) of the support bracket (10); A string fixing rod 43 to which an end of the string 45 is connected and fixed; And a receiving groove 42a through which the string 45 penetrates, one side of the string 45 is in contact with the damping element 41, and the other side of the string fixing rod 43 is fitted thereto. And a damper compression plate 42 for pressing the damping element 41 by the tensile force of 45.
  • damper unit 40 is formed to surround the damper compression plate 42 and the damping element 41 and the damper housing 44 fixed to the outer surface of the head 11 of the support bracket 10. It includes more.
  • the damping element 41 has a damping guide hole 41a through which the string 45 penetrates in a central portion thereof, and is provided on an outer surface of the head 11 of the support bracket 10 facing the damping element 41.
  • the damping element guide protrusion 18 is positioned to be inserted into the damping guide hole 41a to guide deformation of the damping element 41.
  • both sides of the axial displacement restraint body 31 of the fixed shaft cover 30 are in close contact with side surfaces of the displacement confinement block 20 to restrain the axial displacement of the fixed shaft cover 30.
  • 31a) is formed, and an accommodating groove 31b is formed between the restraining surface 31a of the axial displacement restraining body 31 and the shaft body 32, and the damping material 34 is formed in the accommodating groove 31b. Is inserted.
  • the required rigidity for protecting mission equipment of the observation satellite from impact and vibration applied in the launch environment is satisfied, and the insulation performance for protecting the mission equipment from the micro-vibration of the observation satellite in the orbit environment is satisfied.
  • the damper unit further improves the shock vibration damping performance in the launch environment, thereby ensuring structural integrity of mission equipment, and at the same time, perfectly insulates the micro-vibration components generated in the orbit environment and observes the performance of the observation satellite. It is effective to keep the optimum.
  • FIG. 1 is a perspective view of a space cooler microvibration insulation system having a vibration reduction function of the launch environment according to an embodiment of the present invention.
  • FIG. 2 is a diagram illustrating an internal configuration of a displacement restraining block and a damper unit in order to explain a driving shaft and a driving shaft cover in a space cooler micro-vibration insulation system having a launch environment vibration reduction function of FIG.
  • FIG. 3 is a diagram illustrating an internal configuration of the damper unit added to FIG. 2.
  • FIG 4 is a view showing a state before the space cooler microvibration insulation system with a vibration reduction function of the firing environment of Figure 1 is assembled to the cooler.
  • FIG. 5 is a view illustrating a state in which the space cooler microvibration insulation system having a vibration reduction function of the environment of FIG. 1 is assembled to a cooler.
  • Space cooler micro-vibration insulation system (1) having a vibration reduction function of the launch environment according to the present invention is installed in the vibration source of the observation satellite, is connected to the cooler which is the vibration source through a fixed shaft 100 and the support bracket ( 10) provides the durability that shock vibration transmitted from the launch environment of the satellite is not transmitted to the satellite mission equipment through fastening to a specific object (not shown) of the satellite, and minute vibration is transmitted from the orbit environment to the satellite mission equipment. It absorbs and absorbs to prevent transmission.
  • the space cooler micro-vibration insulation system (1) having a vibration reduction function of the launch environment according to a preferred embodiment of the present invention, the one end fixed to the vibration source mounted on the satellite fixed
  • a displacement confinement block 20 for constraining the lateral displacement and the displacement in the lateral direction a support bracket 10 coupled to one side of the displacement confinement block 20, and coupled to an object of the satellite, and a fixed shaft cover 30.
  • a damper unit 40 mounted to an outer surface of the head 11 of the support bracket 10 so as to be disposed radially with respect to the support bracket 10.
  • the support bracket 10 has a head 11 having a receiving space therein, and a pair of left and right legs 13 and 14 extending downward from both left and right sides of the head 11 to impart rigidity of the support bracket 10. ).
  • support bracket holes 17a, 17b, and 17c for fastening the displacement confinement block 20 are formed in the front portion of the head 11. As shown, the support bracket holes 17a, 17b, and 17c are arranged in an equilateral triangle shape so as to be stably fastened with the displacement confinement block 20.
  • the left and right legs 13 and 14 are opened at a stable and centered angle without deteriorating the rigidity around the head 11, and fixing holes 15 are formed in the left leg 13 and the right leg 14, respectively.
  • Fixers 50 such as bolts and screws are fastened to the fixing holes 15, and the support brackets 10 are firmly fixed to specific objects (not shown) of the satellite by the fixers 50.
  • Displacement confinement block 20 is coupled to the support bracket 10 to maintain a fixed force, for this purpose, a plurality of displacement confinement block holes (22a, 22b, 22c) are formed in the displacement confinement block 20.
  • the displacement confinement block holes 22a, 22b and 22c are also arranged in an equilateral triangle shape, and the layout of the displacement confinement block holes 22a, 22b and 22c of the displacement confinement block 20 is a support bracket hole of the support bracket 10. It is the same as the layout which (17a, 17b, 17c) has.
  • Fixer 52 such as a bolt or screw, is fastened to the displacement restraint block holes 22a, 22b, 22c and the support bracket holes 17a, 17b, 17c, and the displacement restraint block 20 is fixed by the fixer 52. It is fixed to the support bracket (10).
  • Displacement constraining block 20 is applied to a plastic-based space material having a high vibration damping properties compared to metal to minimize the external shock transmitted in the launch environment can be particularly absorbed.
  • a planar displacement constraint hole 21 through which a portion (shaft body 32) of the fixed shaft cover 30 surrounding the fixed shaft 100 passes.
  • the shaft body 32 of the fixed side cover 30 is fitted in the plane displacement restraint hole 21 in the axial direction to constrain the motion in the plane direction due to the vibration applied from the firing environment of the fixed shaft 100.
  • the fixed shaft 100 is assembled so that one end is fixed to the mounted vibration source, the fixed shaft 100 is inserted through the support bracket 10 in the axial direction to the displacement confinement block 20, both of the ends One end is formed as a fixed end connected to the vibration source, while the other end is not connected and is formed as a free end exposed through the displacement confinement block 20 to the outside.
  • the fixed shaft 100 is wrapped in the axial direction by the fixed shaft cover 30.
  • the shaft body 32 and the planar displacement restraint hole 21 are positioned not to be in close contact with each other, for example, because the shaft body 32 and the planar displacement restraint hole 21 are positioned. This is because when it is in close contact, the rigid body is constrained and the vibration from the vibration source is transmitted without attenuation, and the transmission from the bottom surface is transmitted to the cooler as it is even in the launch environment.
  • the fixed shaft cover 30 surrounding the fixed shaft 100 is constrained in the planar direction by the plane displacement restraint hole 21 of the displacement confinement block 20, thereby preventing vibrations applied from the vibration source in the launch environment. The occurrence of vibration in the plane direction is blocked.
  • the fixed shaft 100 is installed to surround the fixed shaft cover 30, the fixed shaft cover 30 is an axial displacement restraint body 31 made of a hollow cylindrical shape, and the axial displacement restraint body ( 31 is formed of a shaft body 32 extending from both ends and formed in a hollow cylindrical shape and tightly wraps the fixed shaft 100.
  • the fixed shaft cover 30 may minimize external shocks transmitted from the launch environment by applying a plastic-based space material having a higher vibration damping property than metal.
  • the axial displacement restraint body 31 is in contact with one side of the displacement restraining block 20 coupled to the side portion of the support bracket 10 to prevent the axial movement of the fixed shaft cover 30 surrounding the fixed shaft 100.
  • the diameter of the axis displacement constraint body 31 is formed to be relatively large compared to the diameter of the axis body 32, the constraint surface 31a is formed on the left and right sides of the end of the axis displacement constraint body 31. . Therefore, the restraint surface 31a of the axial displacement restraint body 31 is maintained in close contact with the displacement restraint block 20 by the weight of the cooler 200 (see FIG. 5) in the firing environment on the ground in the gravity state. In this case, the axial movement of the fixed shaft cover 30 may be restrained due to the external shock vibration transmitted strongly in the launch environment.
  • the receiving groove 31b is formed concave between the restraining surface 31a of the shaft displacement restraint body 31 and the outer surface of the shaft body 32, and the damping material 34 is inserted into the receiving recess 31b.
  • a string guide groove 33 is formed on an outer circumferential surface of the fixed shaft cover 30, and the string guide 45 of the damper unit 40 to be described later is positioned in the string guide groove 33.
  • Damper unit 40 is for damping the strong shock and vibration applied from the launch environment of the satellite, is installed on the support bracket 10 to be disposed radially with respect to the fixed shaft cover (30).
  • the damper unit 40 wraps the outer surface of the axial displacement restraint body 31 of the fixed shaft cover 30 in the circumferential direction and has a string 45 having a predetermined tension and a support bracket. And a damper portion connected to the string 45 passing through the string through hole 19 formed in the head 11 of the head 10 to absorb vibration generated from the fixed shaft 100 through the string 45.
  • the damper part has a damping element 41, a damper compression plate 42, a string fixing rod 43 and a damper housing 44.
  • the damping element 41 penetrates the string 45, and one side of the damping element 41 contacts the outer surface of the head 11 of the support bracket 10.
  • the damping element 41 may be a mesh washer of a space viscoelastic material or a shape memory alloy material having high damping performance.
  • a damping guide hole 41a through which the string 45 penetrates is formed in the central portion of the damping element 41, and a damping element guide protrusion 18 to be described later is inserted into the damping guide hole 41a.
  • the string fixing rod 43 has a straight bar shape and the end of the string 45 is connected and fixed.
  • Various examples may be applied to the method in which the string 45 is fixed to the string fixing rod 43, and the present invention is not limited to the specific example.
  • the damper compression plate 42 is arranged so that the string 45 penetrates and one side is in contact with the other side of the damping element 41, and the other side has an accommodating groove in which the string fixing rod 43 is fitted. 42a) is formed to compress the damping element 41 by the tensile force of the string 45.
  • the suspension fixing rod 43 is formed in a cylindrical shape and the receiving groove 42a has a corresponding shape to receive it fixedly, but the present invention is not limited thereto, but the present fixing rod 43 and the corresponding accommodation
  • the groove 42a may have various shapes.
  • the damper housing 44 is formed in a cylindrical shape to surround the damper compression plate 42 and the damping element 41 and is fixedly installed on the support bracket 10 to integrate the components constituting the damper unit 40.
  • the damper housing 44 has a housing hole 46 formed at a side thereof, and the housing hole 46 corresponds to the housing mounting hole 12 formed in the support bracket 10, and thus the housing hole 46 and the housing.
  • the damper unit 40 is fixed to the support bracket 10 through the fixer 54 penetrating the mounting hole 12.
  • Displacement of the fixed shaft 100 and the fixed shaft cover 30 generated from the launching impact of the satellite is transmitted to the string fixing rod 43 through the string 45 passing through the string through hole 19, the string fixing rod 43 is tightly fitted into the receiving groove 42a formed in the damper compression plate 42, whereby the string 45, the string fixing rod 43, and the damper compression plate 42 are integrated, and thus the fixed shaft 100
  • the displacement resulting from the force is immediately transmitted to the damping element 41 in contact with the damper compression plate 42 integrated with the string 45 and the string fixing rod 43.
  • the damping element 41 may be maximized according to the deformation of the damping element 41.
  • a damping element guide protrusion 18 is formed on the outer surface of the head 11 of the support bracket 10 facing the damping element 41 to guide deformation of the damping element 41.
  • the damping element guide protrusion 18 is located inside the damping guide hole 41a formed in the damping element 41.
  • the damping element 41 has a damping element guide protrusion ( It is deformed along the direction of the arc of 18).
  • the shock vibration generated from the vibration source in the launch environment is transmitted to the damping element 41 through the string 45 to be applied from the launch environment through the deformation of the damping element 41.
  • the damper unit 40 effectively insulates even the small vibrations generated from the vibration source so that the extremely sensitive mission equipment can be completely protected from the vibration, which will be described later.
  • FIG 4 and 5 show an application state of the space cooler microvibration insulation system (1) having a vibration reduction function of the launch environment according to an embodiment of the present invention.
  • the aforementioned vibration source is applied to the cooler 200.
  • the space cooler microvibration isolation system 1 having a launch environment vibration reduction function is paired with four, and the space cooler microvibration insulation system 1 with a launch environment vibration reduction function is provided.
  • the transfer line 300 is installed at a 45-degree interval in the wired cooler 200, from which the cooler 200 is stabilized from the space cooler micro-vibration insulation system (1) equipped with a vibration reduction function of the launch environment. Is supported.
  • Space cooler micro-vibration insulation system (1) having four firing environment vibration reduction function is convenient to be assembled is completed only by a simple operation connected to the fixed shaft (100) respectively installed on the fastening portion (210, 220, 230, 240) of the cooler 200 Can be provided.
  • the present invention is not limited thereto, and the present invention is not limited to a specific number as long as it is stably supported by the cooler.
  • the transfer line generated by the impact vibration component applied to the mission equipment in the launch environment of the satellite (observation satellite) The displacement of the 300 is constrained by the displacement confinement block 20 which constrains the axial movement and the axial movement of the fixed shaft 100, and thus the fixed end of the fixed shaft 100 connected to the cooler 200. The displacement exceeding the allowable displacement of the transfer line 300 connected to the cooler 200 is blocked.
  • the fixed shaft 100 is supported by the displacement restraining block 20 and the support bracket 10 coupled thereto in a state in which the fixed shaft 100 is coupled in the axial direction, so that the mission equipment of the observation satellite is applied to the strong external vibration applied in the launch environment. Durability can be firmly maintained even by impact.
  • the damper unit 40 connected to the fixed shaft cover 30 surrounding the fixed shaft 100 in the launch environment can further dampen the shock and vibration components.
  • the micro-vibration cannot play a role for vibration damping in a launch environment in which the vibration environment is more severe than the track environment in which the micro vibration is subjected to vibration insulation. This is because the cooler's own weight in the environment may not be able to maintain the low rigidity support structure to the spring.
  • the triangular plastic cover (displacement control block) and the fixed shaft cover of the same plastic material surrounding the fixed shaft utilize the damping characteristics of the material itself and the energy dissipation caused by friction upon mutual contact due to the vibration of the firing environment. Because there is.
  • vibration energy attenuation effect can be expected from the friction between the plastic materials.
  • the vibration level is relatively high, such as a sinusoidal vibration environment, only the mutual contact between the plastic materials occurs and vibration damping occurs. The effect becomes hard to expect.
  • the impact generated during the collision between the plastic material is transmitted to the cooler which is the vibration source.
  • the damping element 41 and the fixed shaft cover 30 are connected to the strings 45 by the purpose of the vibration damping in the launch environment. Tension is applied to the string 45 connected to 30, and in this case, the damping element 41 may be deformed to achieve vibration energy dissipation. In addition, there is an advantage that the impact is not transmitted to the cooler 200 by preventing excessive collision between the plastic even when the maximum deformation of the damping element 41 connected to the string (45).
  • the cooler 200 when the cooler 200 moves to the nominal position in the orbital environment, the tension of the string 45 connected to the damping element 41 is relaxed, and the cooler 200 permits the transfer line 300 and the cooler 200.
  • the low-rigidity elastic support by the heat pipe 400 provided for the purpose of maintaining the temperature, there is an advantage to effectively insulate the micro-vibration components generated from the cooler 200.
  • the string 45 connected to the damping element 41 and the fixed shaft cover 30 is relaxed, and thus the cooler 200, which is a vibration source, is a heat pipe 400 and a transfer line 300 for thermal control. ), And the natural frequency from the cooler 200 and these support structures is located at a frequency lower than the excitation frequency of the vibration source, so that the vibration insulation can be efficiently performed.
  • it is possible to design to be located at a lower frequency than the removal of the spring disclosed in the prior patent is expected to increase the vibration isolation effect than conventional.
  • the damper unit 40 effectively attenuates the vibration component of the strong impact applied in the firing environment, thereby ensuring the structural integrity of the mission equipment, and at the same time, the string 45 is relaxed in the orbital environment.
  • the present invention has industrial applicability as applied to satellites including observation satellites.

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  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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  • Acoustics & Sound (AREA)
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Abstract

La présente invention concerne un système d'isolation de petites vibrations d'un refroidisseur pour espace ayant une fonction de réduction de vibrations dans un environnement de lancement, comprenant : un arbre de fixation (100), dont une extrémité est reliée de manière fixe à une source de génération de vibrations montée sur un satellite ; un couvercle (30) d'arbre de fixation installé de façon à entourer axialement l'arbre de fixation (100) ; un bloc de retenue de déplacement (20) possédant un trou de retenue de déplacement de plan (21) à travers lequel le corps d'arbre (32) du couvercle (30) d'arbre de fixation peut passer, mais pas un corps de retenue de déplacement d'arbre (31), le trou de retenue de déplacement de plan (21) étant formé sur la partie centrale du bloc de retenue de déplacement (20), une surface latérale du bloc de retenue de déplacement (20) étant en contact avec une extrémité du corps de retenue de déplacement d'arbre (31) ; un palier de support (10) comprenant une tête (110), qui est couplé au bloc de retenue de déplacement (20) et présente un espace de réception formé à l'intérieur de celui-ci pour recevoir le corps de retenue de déplacement d'arbre (31) du couvercle (30) d'arbre de fixation, et des pieds gauche/droit (13, 14) s'étendant à partir de la tête (11) afin d'être élargis à une valeur d'angle prédéterminé ; et une unité d'amortissement (40) incluant une corde (45) montée sur la surface latérale extérieure de la tête (11) du palier de support de manière à être disposées radialement par rapport au corps de retenue de déplacement d'arbre (31) du couvercle (30) d'arbre de fixation et configurée pour appliquer une force de traction constante tout en entourant la surface latérale extérieure du corps de retenue de déplacement d'arbre (31) dans la direction circonférentielle et comprenant une partie d'amortissement reliée à la corde (45) passant à travers un trou traversant (19) de ressort formé dans la tête (11) du palier de support (10) et configuré de façon à absorber, à l'aide de la corde (45), les vibrations générées dans l'arbre de fixation (100).
PCT/KR2014/008553 2013-09-16 2014-09-15 Système d'isolation de petite vibration de refroidisseur pour espace ayant une fonction de réduction de vibrations dans un environnement de lancement Ceased WO2015037954A1 (fr)

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KR1020130110837A KR101445500B1 (ko) 2013-09-16 2013-09-16 발사환경 진동저감 기능을 구비한 우주용 냉각기 미소진동 절연시스템
KR10-2013-0110837 2013-09-16

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KR101809681B1 (ko) 2016-08-19 2017-12-18 조선대학교 산학협력단 발사 구속 장치가 불필요한 냉각기용 진동 절연 시스템
CN111594568B (zh) * 2020-06-03 2021-05-04 北京航宇振控科技有限责任公司 一种多自由度隔振器及隔振系统
US20230407937A1 (en) * 2020-09-25 2023-12-21 William Marsh Rice University Methods and devices for absorbing energy
CN114180106B (zh) * 2021-11-16 2023-08-11 北京卫星制造厂有限公司 一种通风装置
KR102747967B1 (ko) * 2024-08-21 2024-12-27 한화시스템 주식회사 안정화 김발의 저주파수 방진장치

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